• 한국소음진동공학회논문집
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• 제16권12호
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• pp.1252-1261
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• 2006

This paper summarizes theoretical work on the multichannel decentralized feedback control of sound radiation from aircraft trim panels using piezoceramic actuators. The aircraft trim panels are generally honeycomb structures designed to meet the design requirement of low weight and high stiffness. They are resiliently-mounted to the fuselage for the passive reduction of noise transmission. It is motivated by the localization of reduction in vibration of single channel active trim panels. 12-channel decentralized feedback control systems are investigated in terms of the reduction of noise and vibration for three configurations of sensor actuator pairs. Local coupling of the closely-spaced sensor and actuator pairs was modeled using single degree of freedom systems. The multichannel control system is characterized using the state-space model. For the stability point of view, the relative stability or robustness is evaluated by comparing the real part of eigenvalues of the system matrix for the three configurations. The control performance is also evaluated and compared for the three configurations. It is found that the multichannel system can lead to the globalization of the reduction in vibration and radiated noise. It does not appear to yield a significant improvement in the vibration because of decreased gain margin. However, the reduction in the radiated noise is remarkably improved due to the variation of the vibration pattern with the actuation configurations.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2007년도 추계학술대회논문집
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• pp.430-435
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• 2007

소음특성이 서로 다른 군용 항공기 소음과 민간 항공기 소음을 환경부에서 고시한 소음 진동공정시험방법에 의거하여 소음을 측정하고 평가하는데는 개선되어야 할 문제점이 뒤따른다. 따라서 본 연구에서는 민간 항공기와 군용 항공기의 소음특성으로 조사하고 소음 측정 및 평가방법에 대한 문제점들을 고찰하였다. 연구결과로 부터, 민간 항공기나 군용 항공기의 정확한 소음측정을 위해서는 동특성을 빠름(Fast)으로 설정하여 측정하는 것이 바람직한 것으로 확인되었다. 또한 등가 소음도를 측정하여 항공기 소음을 평가하는 방식은 민간 항공기 소음평가시에는 적절하지만, 이를 군용 항공기 소음에 적용하여 평가할 때에는 상당한 오차를 포함하는 것으로 조사되었다. 그리고 군용 항공기 이 착륙지점에서의 소음 지속시간이 대부분 30초를 초과하는 것으로 조사되었기 때문에, 군용 항공기 소음평가시에는 지속시간에 대한 보정이 반드시 반영되어야 할 것으로 사료된다.

• 한국소음진동공학회논문집
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• 제14권3호
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• pp.214-223
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• 2004

This study aim to find an appropriate window for classrooms to provide proper sound insulation against aircraft noise and to achieve this goal, measurements were taken of the sound insulation performance of windows with various thicknesses of inner air space and sound absorption materials in the inner air spaces. As a result of this study the improvement of the sound insulation performance of windows(single, double and triple window) was shown through the analysis and the measuring of windows with these characteristics. These results may be applied to the manufacture of window frames and provide basic data for the improvement of the sound insulation performance of windows.

• 항공우주시스템공학회지
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• 제6권1호
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• pp.13-18
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• 2012

This paper presents a structural health monitoring method of aircraft reciprocating engine using Principal Component Analysis (PCA) which analyzes vibration expressed by Averaged Normalized Power Spectral Density (ANPSD). Because ANPSD of the rotating shaft is sensitive to the rotating speed, this paper proposes to use a post-processing method of ANPSD is used to reduce the sensitivity. The PCA extracts compressed information from the post-processed ANPSDs and the information means the difference between current and normal cases of the engine. The experimental results demonstrate the feasibility and effectiveness of the proposed method to detect abnormal cases of the engine.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2011년도 추계학술대회 논문집
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• pp.244-249
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• 2011

The potential hazards resulting from a low-velocity impact (bird-strike, tool drop, runway debris, etc.) on aircraft structures, such as engine nacelle or a leading edges, has been a long-term concern to the aircraft industry. Certification authorities require that exposed aircraft components must be tested to prove their capability to withstand low-velocity impact without suffering critical damage. In most of the past research studies unloaded specimens have been used for impact tests, however, in reality it is much more likely that a composite structure is exposed to a certain stress state when it is being impacted, which can have a significant effect on the impact performance. And the radiated impact sound induced by impact is analyzed for the damage detection evaluation. In this study, an investigation was undertaken to evaluate the effect in-plane loading on the impact force and sound of composite laminates numerically.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2003년도 추계학술대회논문집
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• pp.710-717
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• 2003

This study aim to find an appropriate window for class rooms to provide proper sound insulation against aircraft noise and to achieve this, measurements were taken of the sound insulation performance of windows with varying thicknesses of inner air space and sound absorption materials in the inner air spaces. As a result of (his study the improvement of the sound insulation performance of windows(single , double and triple window) has been shown through the analysis and the measuring of windows with these characteristics. These results may be applied to the manufacture of window frames and provide data lot the improvement of the sound insulation performance of windows.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.289-291
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• 2006

The noise pollution caused by air traffic is one of the popular environmental issues, which consistently gives rise to public discussion today especially among local residents near airports. But, because there is a growing tendency that large residential areas are constructed in flatlands around airports due to a high population density, the importance of the EIA in connection with aircraft noise is increased to take precautionary measures. Therefore, this paper examines the present status and the improvement plan of aircraft noise impact assessment.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2003년도 춘계학술대회논문집
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• pp.514-519
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• 2003

The aircraft engine is usually supported by rolling element bearings and has a small damping rate, which is vol y sensitive to external force. The high-performance requirement of the rotors leads to complex assembly designs and are more flexible. Squeeze film dampers (SFDs) are introduced to provide damping while crossing the critical speeds and stability to the rotor s :stem. Hence, the focus of the present investigation is on the decision of an optimal size of the flexible rotor system supported by the squeeze film dampers to minimize the maximum transmitted load and unbalance response over a range operating speeds. The enhanced genetic algorithm (EGA), which was developed by authors, is used in the optimization process. This algorithm is based on the synthesis of a modified genetic algorithm and simplex method. The results show significant benefits in using EGA when compared with nonlinear programming (NLP).

• 환경영향평가
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• 제18권1호
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• pp.21-30
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• 2009

The study show that things about the noise control are indicated at The Noise & Vibration Control Act and the other Act. Also, the details program and total government ministries' program for the noise control are indicated what are the advance noise control plan. The study consist of the four part which are "Draw up the environmental noise infrastructure plan; the install shall be done the noisemap & the automatic noise measurement devices", "Resetting of environmental noise standard at the application area and Introduce of indoor noise; the guide for region classification of the noise standard & indoor noise", "Setting of aircraft noise standard and Program of measurement point operation; the noise-assessment-standard shall change from WECPN to new index($L_{den}$, $L_{dn}$, $L_{Aeq\;24h}$) & the operation and control of aircraft noise measurement changes from local environmental office to central control center" and "The method of noise regulation at construction site and the plan on making of standard for vibration regulation; It shall be made that the guideline of construction noise should include a target-construction, noise standard etc & the ministries shall unify control about construction vibration of the blasting vibration". The advance noise-policy will improve efficiency to deal with civil appeal & damage on residents about noise.

• Advances in aircraft and spacecraft science
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• 제6권2호
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• pp.169-187
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• 2019

This work presents a practical detailed finite element (FE) approach for the three-dimensional (3D) free-vibration analysis of actual aircraft and spacecraft-type lightweight and thin honeycomb sandwich panels. It consists of calling successively in $MATLAB^{(R)}$, via a developed user-friendly GUI, a detailed 3D meshing tool, a macrocommands language translator and a commercial FE solver($ABAQUS^{(R)}$ or $ANSYS^{(R)}$). In contrary to the common practice of meshing finely the faces and core cells, the proposed meshing tool represents each wall of the actual hexagonal core cells as a single two-dimensional (2D) 4 nodes quadrangularshell element or two 3 nodes triangular ones, while the faces meshes are obtained simply using the nodes at the core-faces interfaces. Moreover, as the same 2D FE interpolation type is used for meshing the core and faces, this leads to an automatic handling of their required FE compatibility relations. This proposed approach is applied to a sample made of very thin glass fiber reinforced polymer woven composite faces and a thin aluminum alloy hexagonal honeycomb core. The unknown or incomplete geometric and materials properties are first collected through direct measurements, reverse engineering techniques and experimental-FE modal analysis-based inverse identification. Then, the free-vibrations of the actual honeycomb sandwich panel are analyzed experimentally under different boundary conditions and numerically using different mesh basic cell shapes. It is found that this approach is accurate for the first few modes used for pre-design purpose.